Gas turbine engine bleed valve damping guide link
a technology of bleed valve and guide link, which is applied in the direction of gas turbine plants, pump control, fluid engines with non-positive displacement, etc., can solve the problems of low pressure turbine not providing power, more complex assembly, and more prone to durability problems
Active Publication Date: 2020-12-10
RAYTHEON TECH CORP
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Benefits of technology
The patent describes a damping link assembly for a bleed valve of a gas turbine engine. The assembly includes a bleed valve ring, a mechanical fastener, and a damping guide link. The damping guide link is capable of twisting about a third axis when the bleed valve ring is rotated from a first position to a second position. The technical effect of this design is that it provides improved damping of the bleed valve ring movement, reducing vibrations and improving the stability and performance of the gas turbine engine.
Problems solved by technology
During start-up of a gas turbine engine, the low pressure turbine is not providing power to turn the low pressure compressor.
The rigidity of the components requires a number of components, leading to a more complex assembly that may be more prone to durability issues.
Method used
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[0029]A detailed description of one or more embodiments of the disclosed apparatus and method are presented herein by way of exemplification and not limitation with reference to the Figures.
[0030]FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. The fan section 22 drives air along a bypass flow path B in a bypass duct, while the compressor section 24 drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool a...
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A damping link assembly for a bleed valve of a gas turbine engine. The damping link assembly having: a bleed valve ring having a link aperture; a mechanical fastener disposed in the link aperture; and a damping guide link operatively coupled to the mechanical fastener at one end for rotation about a first axis of the mechanical fastener and the damping guide link being operatively coupled to an idler bracket at an opposite end for rotation about a second axis, the damping guide link being capable of twisting about a third axis different from the first axis and the second axis when the bleed valve ring is rotated from a first position to a second position.
Description
BACKGROUND[0001]Exemplary embodiments pertain to the art of gas turbine engines and, more particularly, to a bleed valve guiding assembly for such engines.[0002]During start-up of a gas turbine engine, the low pressure turbine is not providing power to turn the low pressure compressor. Therefore, the low pressure compressor includes a bleed valve to vent the air from the low pressure compressor so that rotating the low pressure compressor is easier. In addition, during acceleration and deceleration, the output of the low pressure compressor may need to be vented in order to maintain pressure balance between the low and high pressure compressors to prevent stalling thereof. These are only two examples of why a bleed valve may be placed in the low pressure compressor.[0003]Bleed systems are challenged to be durable, lightweight and low cost. Prior bleed valve systems require a series of rigid links that guide the valve in an arc as it moves. The rigid link is connected to the valve wi...
Claims
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Patent Timeline
Login to View More IPC IPC(8): F01D17/14F02C9/18F04D27/02
CPCF05D2220/32F04D27/0215F05D2260/56F01D17/141F02C9/18F02C6/08F05D2260/96F05D2260/50F05D2300/501
Inventor LITTLE, JONATHAN D.
Owner RAYTHEON TECH CORP